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A Stability Analysis Method for Aircraft Nonlinear Attitude Control System

A technology for system stability and attitude control, applied in attitude control, control/regulation systems, non-electric variable control, etc.

Active Publication Date: 2019-03-08
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Aiming at the above defects or improvement needs of the prior art, the present invention provides a method for analyzing the stability of the aircraft nonlinear attitude control system, the purpose of which is to express the dynamic coefficient with the dead zone threshold h, and analyze the stability of the nonlinear closed-loop loop, by This solves the problem of multiple simulations and comparison of results in the prior art

Method used

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  • A Stability Analysis Method for Aircraft Nonlinear Attitude Control System
  • A Stability Analysis Method for Aircraft Nonlinear Attitude Control System
  • A Stability Analysis Method for Aircraft Nonlinear Attitude Control System

Examples

Experimental program
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Effect test

Embodiment

[0073] The dynamic coefficient value of the pitch channel corresponding to one flight state of an aircraft is as follows:

[0074] b 1 = 0; b 2 =0.6244; c 1 = 0.0021; c 2 =-0.0015;

[0075] Take h=3 / 180*π, draw the linear part G 1 (s) Nyquist curve and nonlinear partial negative inverse description function curve -1 / N(A)(A≥h), see figure 2 , there is no intersection between the Nyquist curve and the negative inverse description function curve -1 / N(A) of the nonlinear part, the nonlinear system is stable and the amplitude is attenuated. The attitude control system has an amplitude of For the tracking error response of the step command signal, see image 3 .

[0076] Take h=0.5 / 180*π and draw the linear part G 1 (s) Nyquist curve and nonlinear partial negative inverse description function curve -1 / N(A)(A≥h), see Figure 4 , there is an intersection point between the Nyquist curve and the negative inverse description function curve -1 / N(A) of the nonlinear part. T...

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Abstract

The invention discloses an aircraft nonlinear attitude control system stability analysis method, and belongs to the field of aircraft attitude control. According to the method, firstly the power coefficient corresponding to the aircraft flight state is calculated, and a corresponding item is expressed by a dead zone threshold h; and then an aircraft linear part transfer function Nyquist curve and a nonlinear part negative converse descriptive function curve are drawn, if the two curves have no intersection point, the nonlinear system is judged to be stable, the value of the pitch channel dead zone threshold h is designed, or the nonlinear system is judged to be instable. According to the method, the stability judgment method for the closed-loop system under different threshold conditions is given so that the stability judgment basis for the closed loop corresponding to the dead zone threshold is theoretically put forward.

Description

technical field [0001] The invention belongs to the field of aircraft attitude control, and more particularly relates to a stability analysis method for an aircraft nonlinear attitude control system. Background technique [0002] The aircraft attitude control loop includes a relay characteristic link with a dead zone, which is a typical nonlinear feedback control system. The selection of the dead zone threshold h directly affects the stability and dynamic tracking performance of the control loop. From the perspective of improving the tracking accuracy of the attitude control loop, it is required to select a smaller threshold, but too small a threshold will lead to instability of the control loop; too large a threshold will reduce the dynamic tracking performance and accuracy of attitude control. [0003] In the actual engineering design process, the method of mathematical simulation debugging design is widely used, and different dead zone thresholds are set for multiple tim...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCG05D1/0816
Inventor 鲍晓强朱伟陈兴褔陈红艳杨登峰田群方蒋金龙郭一江李焰崔跃军叶昌
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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